CN216709620U

CN216709620U - Foldable undercarriage of unmanned aerial vehicle

Info

Publication number: CN216709620U
Application number: CN202220215017.9U
Authority: CN
Inventors: 赵仑
Original assignee: Weifang Feirui Aviation Technology Co ltd
Current assignee: Weifang Feirui Aviation Technology Co ltd
Priority date: 2022-01-26
Filing date: 2022-01-26
Publication date: 2022-06-10
Anticipated expiration: 2032-01-26

Abstract

A folding undercarriage for an unmanned aerial vehicle relates to the technical field of unmanned aerial vehicles, and comprises a folding undercarriage body and the unmanned aerial vehicle applying the undercarriage; the foldable undercarriage comprises a horizontally arranged mounting plate, and four hinge seats which are oppositely arranged in pairs are fixedly connected at the edge of the lower surface of the mounting plate in a centrosymmetric manner; a swing connecting rod is hinged to the end face of one side of each hinge seat, and a rotary supporting rod is hinged to the swing tail end of each swing connecting rod; a telescopic connecting rod is hinged on the end face at the other side of the hinged seat and is opposite to the swinging connecting rod; a telescopic supporting rod is arranged between the mounting plate and the swinging connecting rod. The utility model solves the problems that the unmanned aerial vehicle landing gear in the traditional technology is easy to collide, the wind resistance is increased, the flight stability is reduced and the landing impact force is larger during low-altitude flight.

Description

Foldable undercarriage of unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a folding undercarriage of an unmanned aerial vehicle.

Background

The unmanned plane is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The automatic pilot and the program control device are installed on the airplane without a driver. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar. Unmanned aerial vehicles can be divided into several types according to their functions: "password" unmanned aerial vehicle, multi-functional unmanned aerial vehicle, long term staying empty unmanned aerial vehicle, anti-missile unmanned aerial vehicle, early warning unmanned aerial vehicle, stealth unmanned aerial vehicle, miniature unmanned aerial vehicle, survey and drawing unmanned aerial vehicle and take photo by plane unmanned aerial vehicle. Surveying and mapping unmanned aerial vehicles and aerial photography unmanned aerial vehicles are generally contacted in life, wherein the surveying and mapping unmanned aerial vehicles can autonomously fly and shoot according to a preset air route, remote sensing monitoring data and low-altitude video monitoring are provided in real time, and the remote sensing monitoring system has the characteristics of strong maneuverability, convenience, low cost and the like, and the acquired high-resolution remote sensing data are used for dynamic supervision, marine environment monitoring, resource protection and the like in sea areas; and the unmanned aerial vehicle that takes photo by plane has integrateed high definition photography camera device's remote control aircraft, is fit for the shooting of movie & TV propaganda piece and bird's eye view etc.. The unmanned aerial vehicle has wide application, low cost and higher efficiency; no casualty risk; the life ability is strong, the maneuverability is good, the use is convenient, the device plays an extremely important role in modern war and has a wider prospect in the civil field.

The undercarriage is an accessory device used for supporting an airplane when the lower part of the unmanned aerial vehicle is used for taking off or landing, and the undercarriage is an indispensable part of the unmanned aerial vehicle as a part which plays the sole supporting role for the whole unmanned aerial vehicle.

The following problems often exist in the use of current unmanned aerial vehicle undercarriage:

1. the existing landing gear of the unmanned aerial vehicle is usually directly fixed on the lower part of the unmanned aerial vehicle and always keeps supporting and unfolding states, so that the unmanned aerial vehicle can collide with obstacles under certain special flight scenes (such as low-altitude flight), and the structure of the unmanned aerial vehicle is damaged.

2. In addition, the landing gear in the unfolding state enables the wind resistance of the unmanned aerial vehicle to be increased during flying, the energy consumption is increased, and the stability in the flying process cannot be guaranteed.

3. The existing undercarriage is not provided with a lifting buffer mechanism generally, so that the impact force generated when the unmanned aerial vehicle rises and falls can not be relieved, and the structural stability of the unmanned aerial vehicle can be influenced.

In view of the above, the prior art is obviously inconvenient and disadvantageous in practical use, and needs to be improved.

SUMMERY OF THE UTILITY MODEL

Aiming at the defects in the prior art, the utility model provides an unmanned aerial vehicle folding undercarriage which is used for solving the problems that the unmanned aerial vehicle undercarriage in the traditional technology is easy to collide, the wind resistance is increased, the flight stability is reduced and the landing impact force is large when the unmanned aerial vehicle undercarriage flies at low altitude.

In order to achieve the purpose, the utility model provides the following technical scheme:

the utility model provides a foldable undercarriage of unmanned aerial vehicle, includes the unmanned aerial vehicle of folding undercarriage body and applied this undercarriage.

Preferably, the folding undercarriage comprises a horizontally disposed mounting plate.

As an optimized scheme, a vertically arranged spring shock absorber is fixedly connected to the center of the upper surface of the mounting plate.

As an optimized scheme, the lower end face center of the unmanned aerial vehicle is fixedly connected with an installation buckle.

As an optimized scheme, the upper end of the spring damper is clamped in the mounting buckle, so that the undercarriage is integrally mounted on the unmanned aerial vehicle.

As a scheme of optimizing, the upper surface edge of mounting panel still the rigid coupling have a plurality of to be centrosymmetric buffer spring, buffer spring's upper end rigid coupling has the cushion socket, the up end of cushion socket with unmanned aerial vehicle's lower terminal surface offsets, spring damper reaches buffer spring's setting can reduce the impact force when unmanned aerial vehicle descends to play the guard action to unmanned aerial vehicle inner structure.

As an optimized scheme, four hinge seats which are arranged oppositely in pairs are fixedly connected at the edge of the lower surface of the mounting plate in a centrosymmetric manner.

As an optimized scheme, a swinging connecting rod is hinged and installed on one side end face of each hinge seat.

As an optimized scheme, the swinging tail end of the swinging connecting rod is hinged with a rotating supporting rod.

As an optimized scheme, the rotary supporting rod is arranged on the end face of the swing connecting rod on the same side as the hinge seat.

As an optimized scheme, a telescopic connecting rod is hinged to the end face of the other side of the hinged seat opposite to the swinging connecting rod, the extending end of the telescopic connecting rod is hinged to one end of the rotating supporting rod, and the rotation of the rotating supporting rod can be controlled through the stretching of the telescopic connecting rod, so that the rotating supporting rod is stored and unfolded.

As an optimized scheme, the lower surface of the mounting plate is provided with a containing groove corresponding to the hinge seat, and the containing groove is formed in the inner side of the hinge seat.

As an optimized scheme, an installation groove is formed in the side wall, opposite to the swing of the installation plate, of the swing connecting rod.

As an optimized scheme, the inner top surface of the accommodating groove and the inner wall of the mounting groove are fixedly connected with hinge seats respectively.

As an optimized scheme, a telescopic supporting rod is hinged between the hinge seats, and the telescopic supporting rod can control the swinging of the swinging connecting rod through stretching, so that the storage and the expansion of the swinging connecting rod are controlled.

Compared with the prior art, the utility model has the beneficial effects that:

the landing gear in the utility model adopts a foldable design on the whole: the swing that can realize swing connecting rod and rotation support pole through the flexible cooperation of flexible connecting rod and flexible bracing piece expandes and rotates and accomodate to realize folding of unmanned aerial vehicle flight in-process undercarriage and pack up, the windage when having reduced unmanned aerial vehicle flight has guaranteed flight stability, and has reduced unmanned aerial vehicle's flight volume on the whole, has avoided the danger of striking the barrier when low-altitude flight.

According to the utility model, the buffering and damping mechanism is arranged at the joint of the undercarriage and the unmanned aerial vehicle, and the impact force of the unmanned aerial vehicle during landing is reduced through the spring damper and the buffer spring, so that the unmanned aerial vehicle is protected to a certain extent.

Drawings

In order to more clearly illustrate the detailed description of the utility model or the technical solutions in the prior art, the drawings that are needed in the detailed description of the utility model or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.

FIG. 1 is a schematic structural view of the unmanned aerial vehicle in an unfolded state during landing;

fig. 2 is a schematic structural view of the unmanned aerial vehicle in a storage state during flight.

In the figure: 1-unmanned aerial vehicle, 2-mounting plate, 3-spring damper, 4-mounting buckle, 5-buffer spring, 6-buffer seat, 7-hinged seat, 8-swinging connecting rod, 9-rotating supporting rod, 10-telescopic connecting rod, 11-accommodating groove, 12-mounting groove, 13-hinged seat and 14-telescopic supporting rod.

Detailed Description

Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.

As shown in fig. 1 to 2, a folding landing gear of an unmanned aerial vehicle comprises a folding landing gear body and an unmanned aerial vehicle 1 applying the landing gear.

The folding undercarriage comprises a horizontally arranged mounting plate 2.

The spring damper 3 which is vertically arranged is fixedly connected to the center of the upper surface of the mounting plate 2.

The lower terminal surface center department rigid coupling of unmanned aerial vehicle 1 has installation buckle 4.

The upper end of spring damper 3 clamps in installation buckle 4 to fold undercarriage integral erection on unmanned aerial vehicle 1.

The last surface edge of mounting panel 2 still the rigid coupling have a plurality of to be centrosymmetric buffer spring 5, and buffer spring 5's upper end rigid coupling has buffer seat 6, and buffer seat 6's up end offsets with unmanned aerial vehicle 1's lower terminal surface, and the setting of spring damper 3 and buffer spring 5 can reduce the impact force when unmanned aerial vehicle 1 descends to play the guard action to 1 inner structure of unmanned aerial vehicle.

The edge of the lower surface of the mounting plate 2 is fixedly connected with four hinge seats 13 which are arranged in a pairwise opposite manner and are centrosymmetric.

And a swing connecting rod 8 is hinged and mounted on one side end face of each hinge seat 13.

The swinging tail end of the swinging connecting rod 8 is hinged with a rotating supporting rod 9.

The rotary supporting rod 9 is arranged on the end face of the swing connecting rod 8 on the same side with the hinge seat 13.

The other end face of the hinged seat 13 is hinged with a telescopic connecting rod 10 opposite to the swinging connecting rod 8, the extending end of the telescopic connecting rod 10 is hinged with one end of the rotating supporting rod 9, and the rotation of the rotating supporting rod 9 can be controlled by the stretching of the telescopic connecting rod 10, so that the rotating supporting rod 9 can be stored and unfolded.

The lower surface of the mounting plate 2 is provided with a storage groove 11 corresponding to the hinge base 13, and the storage groove 11 is arranged on the inner side of the hinge base 13.

The side wall of the swing connecting rod 8 opposite to the swing of the mounting plate 2 is provided with a mounting groove 12.

The inner top surface of the receiving groove 11 and the inner wall of the mounting groove 12 are respectively and fixedly connected with a hinge seat 13.

A telescopic supporting rod 14 is hinged between the hinge seats 13, and the telescopic supporting rod 14 can control the swing of the swing connecting rod 8 through stretching, so that the storage and the expansion of the swing connecting rod 8 are controlled.

When the utility model is used: when the unmanned aerial vehicle lands, firstly, the swinging connecting rod 8 swings by 90 degrees and is supported and fixed through the extension of the telescopic supporting rod 14, then the telescopic connecting rod 10 is driven to contract to drive the rotating supporting rod 9 to rotate by 90 degrees to a horizontal position to perform landing support on the unmanned aerial vehicle, and the spring shock absorber 3 and the buffer spring 5 can reduce the landing impact force during landing; when unmanned aerial vehicle flies, telescopic link 10 extends, and telescopic support rod 14 contracts, will rotate bracing piece 9 and swing connecting rod 8 and pack up in proper order.

Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present invention, and not for limiting the same, although the present invention is described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: it is to be understood that modifications may be made to the above-described embodiments, or equivalents may be substituted for some or all of their features, without departing from the spirit and scope of the present invention.

Claims

1. The utility model provides a foldable undercarriage of unmanned aerial vehicle which characterized in that: the landing gear comprises a folding landing gear body and an unmanned aerial vehicle (1) applying the landing gear;

the folding undercarriage comprises a horizontally arranged mounting plate (2), and four hinge seats (13) which are arranged in pairs and are opposite to each other are fixedly connected at the edge of the lower surface of the mounting plate (2) in a centrosymmetric manner;

a swing connecting rod (8) is hinged to one side end face of each hinge seat (13), and a rotary supporting rod (9) is hinged to the swing tail end of each swing connecting rod (8);

a telescopic connecting rod (10) is hinged on the end face of the other side of the hinged seat (13) opposite to the swinging connecting rod (8);

a telescopic supporting rod (14) is arranged between the mounting plate (2) and the swinging connecting rod (8).

2. The folding undercarriage for unmanned aerial vehicles of claim 1 wherein: the lower terminal surface center department rigid coupling of unmanned aerial vehicle (1) has installation buckle (4), the upper surface center department rigid coupling of mounting panel (2) has spring damper (3) of vertical setting, the upper end of spring damper (3) clamp in installation buckle (4).

3. The folding undercarriage for unmanned aerial vehicles of claim 2 wherein: the upper surface edge of mounting panel (2) still the rigid coupling have a plurality of to be centrosymmetric buffer spring (5), the upper end rigid coupling of buffer spring (5) has buffer seat (6), the up end of buffer seat (6) with the lower terminal surface of unmanned aerial vehicle (1) offsets.

4. A folding undercarriage for unmanned aerial vehicles according to claim 3 wherein: the rotary supporting rod (9) is arranged on the end face of the swing connecting rod (8) on the same side as the hinge seat (13).

5. The folding undercarriage for unmanned aerial vehicles of claim 4 wherein: on the lower surface of mounting panel (2) with articulated seat (13) correspond has seted up and has accomodate groove (11), accomodate groove (11) set up in the inboard of articulated seat (13).

6. The folding undercarriage for unmanned aerial vehicles of claim 5 wherein: the side wall of the swing connecting rod (8) opposite to the side wall of the mounting plate (2) in a swing mode is provided with a mounting groove (12).

7. The folding undercarriage for unmanned aerial vehicles of claim 6 wherein: the inner top surface of the accommodating groove (11) and the inner wall of the mounting groove (12) are fixedly connected with a hinge seat (13) respectively.

8. The folding undercarriage for unmanned aerial vehicles of claim 7 wherein: two ends of the telescopic supporting rod (14) are respectively hinged on the hinge seats (13).